Demonstration of tethered hovering flight of HTTP-3AT hybrid rocket

Wei, Shih-Sin; Lee, Meng-Che; Huang, Jie Rong; Lu, Yueh Hsin; Kang, Che-Hao; Kao, Sho-Tsung; Lu, Shao-Jung; Huang, Chang-Hsiang; Zhan, Jun-Jian; Chen, Zuo-Ren; Wang, Andrew; Chou, T. H.; Lai, Alfred; Lee, Yang; Ho, Ming-Tzu; Lin, Hsin‐Piao; Wu, Jong-Shinn

doi:10.1016/j.actaastro.2021.08.042

Cited by 21 publications

(8 citation statements)

References 18 publications

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“…To close this discussion on recent HRE achievements, let us consider the first example of (tethered) hovering of an HRE rocket [73]. In 2020, the team of the ARRC successfully demonstrated stable 25 s hovering of the H 2 O 2 /Polypropylene rocket 3 m above the ground using both attitude and position controls.…”

Section: Discussion On Recent Milestonesmentioning

confidence: 99%

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Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits, hybrid propulsion has yet to achieve its full potential in space applications. In recent years, the research on hybrid propulsion has gained enormous momentum in both academia and industry. Recent accomplishments such as the altitude record for student rockets (64 km), the launch of the first electric pump-fed hybrid rocket, and a successful 25 s hovering test highlight the potential of hybrid rockets. However, although the hybrid community is growing constantly, industrial utilizations and in-space validations do not yet exist. In this work, we reassess the possibilities of hybrid rocket engines by presenting potential fields of applications from the literature. Most importantly, we identify the technical challenges that hinder the breakthrough of hybrid propulsion in the space sector and evaluate the technologies and approaches necessary to bridge the gaps in hybrid rocket development.

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Section: Discussion On Recent Milestonesmentioning

confidence: 99%

“…Other successful throttleable hybrids have been reported in ranges of 3:1 [69,70] with soft landing experiments (see Figure 3), roughly 4:1 (from around 700 N) [71], 8.88:1 (from 950 N) [72], 1.66:1 [73], and 10:1 [74,75]. Ruffin et al [76] achieved throttling ratios of 12.6:1 and Bhadran et al [77] throttled down to 5.5:1.…”

Section: Throttlingmentioning

confidence: 92%

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Glaser,

Hijlkema,

Anthoine

2023

Aerospace

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“…Due to their unique structural advantages, HRMs combine the benefits of both solid and liquid propulsion systems, resulting in high safety performance in the storage and transportation of the oxidizer and fuel. Additionally, HRMs enable precise control of the oxidizer flow, enabling on-demand start–stop functionality and adjustable thrust capabilities. , Consequently, HRMs have found wide-ranging applications in sub-orbiting spaceships, sounding rockets, and target missiles. − However, there are limitations hindering the further commercial development of HRMs. The internal combustion process of the solid–liquid hybrid engine follows a typical diffusion combustion process, where the oxidizer may not effectively combust with the solid fuel.…”

Section: Introductionmentioning

confidence: 99%

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

Chen,

Fu,

Yang

et al. 2024

Langmuir

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Despite hybrid rocket motors offering distinct advantages over solid or liquid rocket motors, their low regression rate and insufficient combustion efficiency remain significantly unimproved. This study focuses on the effects of the helix lead on the regression rate distribution and combustion efficiency of vat-polymerized fuel grains with a spiral star port for a hybrid rocket. Both experimental and numerical investigations were conducted to study the combustion characteristics and regression rate distribution of three-dimensional (3D) print grains. Spiral star grains with varying helix leads of 60, 90, and 120 mm were fabricated using light-curing 3D printing technology. A 3D simulation model was developed to obtain the temperature distribution, species mass distribution, and combustion efficiency. Furthermore, firing tests were performed on a two-dimensional radial hybrid combustion test stand to measure the regression rate. Digital image processing of computed tomography images was used to determine the regression rate. Simulation results indicated that the spiral star grain port helps to improve the combustion efficiency compared with those seen with round tube and straight star port grains. With an increase in the axial distance, the flame zone gradually shrinks, and the smaller the helix lead, the faster the shrinkage. At a mass flow rate of 1.50 g/s for oxygen, the regression rate of the spiral star grains is significantly higher than that of the straight star grain and the conventional round tubular grains, and the regression rate gradually increases with a decrease in the helix lead. This finding is expected to solve the problem of the low regression rate of solid fuels with spiral star pore-shaped grains prepared by the light-curing 3D printing method.

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“…Hybrid rocket motor, consisting of liquid propellant and solid grain, has excellent variable thrust and multiple restart capability [1][2][3][4]. The conventional supply system of hydrogen peroxide rocket engine is pressurized by a gas cylinder and a storage tank, which forces the system to use a heavy gas cylinder and storage tank [5,6].…”

Section: Introductionmentioning

confidence: 99%

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

Tian

et al. 2023

J. Phys.: Conf. Ser.

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Hydrogen peroxide electric pump supply system can provide an improvement to hybrid rocket motor performance. Due to the physical and chemical properties of hydrogen peroxide, a canned pump scheme is more suitable to be used in hybrid rocket motor. The high-temperature liquid between the rotor and stator of the electric pump, returning to the inlet of the inducer, has a considerable influence on the anti-cavitation performance. The numerical simulation results show that the optimal reflux scheme is different when the inlet pressure range of the inducer is different. When the inlet pressure of the inducer is 0.4 MPa, the performance of the inducer is less affected by the reflux schemes, and the optimal scheme is the axial scheme in the simulation. When the inlet pressure is 0.12 MPa and there is a large cavitation area in the inducer, the radial reflux scheme is better than the axial and mixed reflux. When the inlet pressure is 0.1 MPa and the cavitation areas almost extend to the whole blade passage, the radial reflux scheme is much better than the axial and mixed reflux.

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Demonstration of tethered hovering flight of HTTP-3AT hybrid rocket

Cited by 21 publications

References 18 publications

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Bridging the Technology Gap: Strategies for Hybrid Rocket Engines

Combustion Characteristics of Vat-Photopolymerized Fuels with a Spiral Star Port for Hybrid Propulsion

The effect of reflux schemes in hydrogen peroxide electric pump on anti-cavitation of inducer

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